The hydrogen bubbles that produced the velocity profilesin Fig.  are quite small, D ≈0.01 mm. If the hydrogen–water interface is comparable to air–water and the watertemperature is 30 ° C, estimate the excess pressure withinthe bubble.

Q: Engineers call the supersonic combustion in a scramjetengine almost miraculous, “like lighting a…

A: Given Data: The area at section 1 and 4 is: A1=1 m2. The area at section 2 and 4 is: A2=0.2 m2. The…

Q: Air (kinematic viscosity, v = 1.79 × 10 m?/s at 50°C) with a speed of 12 m/s and Water (u = 1.14 x…

A:

Q: Q2 (a) In designing a nozzle why nozzle angle is not zero. Explain with the help of sketch. Q2 (b)…

A: Nozzle :- Nozzle is an device which are used to increase the kinetic energy and convert in to heat.…

Q: The upstream flow properties are T1= 280 K and V= 2000 mph. What is downstream Mach number?

A: The Mach number, M, is defined as the ratio of the actual velocity V to the sonic velocity c, M=Vc…

Q: Air at 20 °C and 1 atm flows past a smooth flat plate at Uoo =20.1 m/s (below figure). A pitot…

A:

Q: What is the maximum pressure in the sound wave generated by a rigid door slammed to stop impulsively…

A: Given Data  Speed, V= 10 m/s Smax=10 nm  Density = 1.2 Kg/m3. ω=2πf=2π(200)=400π  rad/s

Q: Use these data to estimate (a) the speed of sound (m/s) and (b) the bulk modulus (MPa) of gasoline…

A:

Q: Air flows at high speed through a Herschel venturi monitoredby a mercury manometer, as shown in Fig.…

A: Given data, Determine the density of fluid by using the ideal gas equation,

Q: An explosion in air, k = 1.4, creates a spherical shock wave propagating radially into still air at…

A: (a) Calculate the Mach number. p2p1=1+2γγ+1M2-11400101.3=1+21.41.4+1M2-1M=3.4625

Q: A supersonic inlet is sketched below and contains an oblique shock wave followed by a normal shock…

A: Given:M1=3T1=300 KP1=101.3 KPa

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M 3; 1 atm, and p, = 1…

A: Given: Normal shock wave in air. The upstream condition are: M1=3P1=1 atmρ=1.23 kg/m3

Q: Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23…

A: Given: The density of fluid at sea level, ρ = 1.23 kg/m3 = 0.002377 slug/ft3 The pressure at sea…

Q: A certain water flow at 20 ° C has a critical cavitationnumber, where bubbles form, Ca ≈ 0.25, where…

A: Given: The critical cavitation number of the water flow is Ca=0.25 The atmospheric pressure is pa=1…

Q: In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile #…

A:

Q: Consider a normal shock wave in air The upstream conditions are given by M = 3; 1 atm, and p1 M2,…

A: From the given data: p1=1 atm = 101.32 kPaInitial temperature is given…

Q: An airflow at Mach 0.6 passes through a channel with a cross-sectional area of 50 cm?. The static…

A: Please find the solution below

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

A:

Q: With the aid of diagrams, explain what are Mach waves and how they are formed.

A:

Q: The SR-71 Blackbird is the fastest production plane capable of reaching speeds of more than Mach 3,…

A: GivenMach no. for blackbird M=3specific heat of air R=287j/kg.kspecific heat ratio γ=1.4To…

Q: diheoat = 8 cm 1 2 Exit Po da = 18 cm Shock wave Figure 4 [Gambarajah 4] (i) Determine the Mach…

A: The nozzle is a device that has varying cross-sections, in which pressure is reduced by expansion…

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

A:

Q: Methane, approximated as a perfect gas, is compressedadiabatically from 101 kPa and 20°C to 300 kPa.…

A: Write the given data: Write the properties of methane gas.

Q: Consider a business jet, like the Gulfstream G550, flying at a standard altitude of 30,000 f and V1…

A: Given:Standard altitude, h=30000 ft or 9144 mvelocity of stream, V1=525 mph or 145.833 m/s

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; P1 = 1 atm, and…

A: Since you have posted a question with multiple subparts, we will solve the first three subparts for…

Q: An explosion occurs which creates a plane normal shock wave propagating into a region of air that is…

A: Given:The stagnation pressure, Po = 1.0135 x 105 PaThe stagnation temperature, To = 290 KThe speed…

Q: Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of…

A: Given data Mach number = 0.35 Altitude = 30000 ft Weight = 73000 lb S = 950 ft2 AR = 5.92  CD,0 =…

Q: Air flows isentropically in a channel. Properties at section1 are V1 = 250 m/s, T1 = 330 K, and p1 =…

A: a) The expression for the isentropic flow is: Here, P2 represents the pressure at section 2, P1…

Q: A supersonic flow at M = 3, T1 = 295 K, and pi = 3 atm is deflected upward through a compression…

A:

Q: For the container of Fig. P3.116 use Bernoulli’s equation toderive a formula for the distance X…

A: let's suppose 1 upstream at free surface of container & 2 at nozzle exit. using Bernoulli's…

Q: Estimate the speed of sound of carbon monoxide at 200-kPa pressure and 300°C in m/s.

A: Given: The molecular weight of CO=28 kCO=1.4 RCO=RMCO=831428=297 m2/s2KT=300+273=573

Q: In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile #…

A:

Q: An experimental scramjet aircraft is flying at an altitude of 25,000m at Mach 5. Considering it;s…

A: Given: M1 =5  delta = 5 deg P2/P1 = ?

Q: A team of scientists wants to produce a supersonic flow in the test section of a wind tunnel, at…

A: We are assuming the air flow to be isentropic,and it has ideal gas properties.Now,i)Mass flow…

Q: Air flows from a tank through a nozzle into the standardatmosphere, as in Fig.  A normal shock…

A: Given data as per the question Area of throat =10 cm2 Area at exit =14 cm2 The temperature of air…

Q: A cylinder 4 ft in diameter is placed in an air stream where the free-stream velocity is 100 ft/s.…

A: Given: r= 4 ftU∞=100 ft/sθ1=45°θ2=135°

Q: 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle…

A:

Q: An airfoil is in a freestream where p.(assigned altitude)atm, p(density) (assigned altitude) kg/m3,…

A: GivenP∞=36.22atmP=0.5atmV∞=980m/s ρ=36.22kg/m3

Q: Air flows through a converging–diverging nozzle betweentwo large reservoirs, as shown in Fig.  A…

A: Given Data: The reading of manometer is, h=15 cm. The pressure at the nozzle inlet is, P0=300 kPa.…

Q: Show that for isentropic flow of a perfect gas if a pitot- static probe measures Po, p, and Tg, the…

A: Given: Isentropic flow of a perfect gas

Q: A jet of ethylene exists a 40 mm diameter nozzle into still air at 300K and 1 atm. Compare the…

A:

Q: A typical carbon dioxide tank for a paintball gun holdsabout 12 oz of liquid CO2. The tank is fi…

A: Given: mCO2=12 ozP0=850 psiadexit=0.050 in

Q: Consider the flow past a 30° expansion corner, as sketched in the figure below. The upstream…

A:

Q: Air at Ma1 = 2.0 and p1 = 100 kPa undergoes an isentropicexpansion to a downstream pressure of 50…

A: GivenMach no. before the turn, Ma1=2 Pressure before the turn, p1=100 kPa Pressure before the turn,…

Q: Derive on an expression for the propeller thrust T, which depends on speed V, Dia. D, density p,…

A: It is required to derive an expression for propeller thrust which depends on speed, diameter,…

Q: Supersonic airflow takes a 5° expansion turn, as inFig.  Compute the downstream Mach number…

A: